General Electric Company

Other

Harold Edward Miller

Vivek Venugopal Badami

Daniel White Sexton

Konrad Roman Weeber

James Michael Fogarty

Richard Nils Dawson

Nilesh Tralshawala

Philip Lynn Andrew

John David Stampfli

Sameer Vittal

Paul Thomas Marks

Joseph Anthony Cotroneo

Daniel Robert Dwyer

Ronald Richard Wesorick

Rebecca Ann Nold

Ronald W Cheney

Phillip Lynn Andrew

A creep life management system includes at least one sensor apparatus coupled to a first component. The at least one sensor apparatus is configured with a unique identifier. The creep life management system also includes at least one reader unit coupled to a second component. The at least one reader unit is configured to transmit an interrogation request signal to the at least one sensor apparatus and receive a measurement response signal transmitted from the at least one sensor apparatus. The creep life management system further includes at least one processor programmed to determine a real-time creep profile of the first component as a function of the measurement response signal transmitted from the at least one sensor apparatus.

Creep life management system for a turbine engine and method of operating the same

The present invention provides systems and methods of removing heat from internal areas of a turbomachine. Embodiments of the present invention may incorporate a suction device and a control system. Operatively, these elements may collectively discharge remnants of a heated fluid and/or gas from those internal areas.

System and method for removing heat from a turbomachine

A turbine bucket tip clearance control system includes a rotor assembly having a rotor supporting a plurality of axially spaced wheels, each wheel mounting an annular row of buckets, the annular row of buckets on at least one of the plurality of axially-spaced wheels having a radially outer tip shroud provided with at least one seal tooth. A stator assembly includes a radially inwardly facing, axially-stepped surface, formed with radially inner and outer seal surfaces connected by a shoulder. The stator assembly and rotor assembly are moveable axially relative to each other, enabling selective positioning of the at least one seal tooth radially opposite one of the radially inner and outer seal surfaces to thereby selectively alter a clearance gap between the at least one seal tooth and the radially inward facing axially-stepped surface.

Active tip clearance control for shrouded gas turbine blades and related method

A method of operating a power generation system and a power generation system are provided. The method includes coupling at least one electrical generator to at least one prime mover, wherein the at least one generator includes at least one of a stator and a rotor wherein at least one of the stator and the rotor includes superconducting windings therein, and coupling at least one cryogenic refrigeration system to the superconducting windings, wherein the at least one cryogenic refrigeration system is coupled in flow communication with the superconducting windings to facilitate reducing an operating temperature of the superconducting windings. The system includes at least one prime mover, at least one electrical generator rotatably coupled to the at least one prime mover, wherein the generator includes at least one of a stator and a rotor wherein at least one of the stator and the rotor includes a plurality of superconducting windings therein, and at least one cryogenic refrigeration system in flow communication with the superconducting windings.

Methods and system for power generation

A blade assembly is provided for installation in a rotor wheel slot having a slot neck in communication with a slot base cavity having first and second slot flank walls and a slot floor. The blade assembly comprises a blade element having an airfoil portion and a base portion configured for insertion into the rotor wheel slot through the slot neck. The blade assembly also comprises at least one filler piece configured for insertion into the rotor wheel slot through the slot neck. The at least one filler piece is also configured for positioning intermediate the base portion and the first slot flank wall to secure the base portion within the rotor wheel slot.

Method and system for replacing a compressor blade

A gas turbine operational strategy is provided for the optimization of ISO-Day rated performance. The invention is realized by setting the nominal operating line equal to or slightly below the operating limit line, so that ISO full load performance is maximized. Thus, the first stage turbine nozzle throat area is sized such that, without inlet bleed heat addition, and at Base-Load pressure ratio and firing temperature, the compressor operates within its operational limits on a ISO day. As ambient conditions change, levels of inlet bleed heat and firing temperature are controlled and the inlet guide vane angle is set whereby the nominal operating line is equal to or slightly below the operating limit line.

Method of operation of industrial gas turbine for optimal performance

The knee brace of the present invention comprises a pair of elongated articulated assemblies adapted to embrace the interior and exterior surfaces of the knee. Each assembly comprises an upper member, a lower member, and a hinge pivotally interconnecting the upper and lower members. The upper and lower members each include arcuate gear surfaces which intermesh during articulated movement of the members and the hinge. The gear surfaces include annular flanges which reinforce the gear teeth on the gear surfaces.

Growing community of inventors

Glenville, NY, United States of America

Harold Edward Miller